CN111108289A

CN111108289A - Injection method and apparatus for connecting and repairing shear webs

Info

Publication number: CN111108289A
Application number: CN201880063099.6A
Authority: CN
Inventors: D.J.丹尼尔森
Original assignee: General Electric Co
Current assignee: General Electric Renovables Espana SL
Priority date: 2017-07-27
Filing date: 2018-07-19
Publication date: 2020-05-05
Anticipated expiration: 2038-07-19
Also published as: EP3658768B1; WO2019023031A1; MX2020000779A; US20190032632A1; DK3658768T3; US10544776B2; EP3658768A1; CN111108289B; EP3658768A4; ES3036079T3

Abstract

A method and apparatus for connecting and repairing shear webs comprising the method steps of: dry-fitting a shear web insert in the rotor blade assembly to establish a peripheral gap at an angled peripheral interface between the shear web insert and the rotor blade assembly, the angled peripheral interface being positioned between the shear web insert and at least one adjacent surface of the first shear web, the second shear web, the first side of the rotor blade assembly, and the second side of the rotor blade assembly; and then injecting a bonding paste into the peripheral gap. The rotor blade assembly may include an attachment device having at least one prefabricated clamp.

Description

Injection method and apparatus for joining and repairing shear webs

Technical Field

The present subject matter relates generally to wind turbines, and more particularly to a bond paste injection method and apparatus for joining and repairing shear web joints in blades.

Background

Wind power is considered one of the cleanest, most environmentally friendly energy sources presently available, and wind turbines have gained increased attention in this regard. Modern wind turbines typically include a tower, generator, gearbox, nacelle, and one or more turbine blades. The turbine blades extract kinetic energy from the wind using known airfoil (foil) principles and transmit the kinetic energy through rotational energy to turn a shaft coupling the rotor blades to a gearbox (or directly to the generator if a gearbox is not used). The generator then converts the mechanical energy to electrical energy, which may be deployed to a utility grid.

To ensure that wind power remains a viable energy source, efforts have been made to increase energy output by modifying the size and capacity of wind turbines. One such modification is to increase the length of the rotor blade. However, as is generally known, the deflection of a rotor blade is a function of the blade length along with the wind speed, turbine operating conditions and blade stiffness. Thus, longer rotor blades may be subjected to increased deflection forces, particularly when the wind turbine is operated in high velocity wind conditions. These increased deflection forces not only produce fatigue on the rotor blades and other wind turbine components, but may also increase the risk of the rotor blades impacting the tower.

To increase the length of a wind turbine rotor blade without adversely affecting the aerodynamic design, blade inserts may be used to increase the span of the rotor blade by an amount generally corresponding to the overall length of the blade insert. Additionally, for rotor blades that generally include a suction side shell and a pressure side shell and that are typically formed using a molding process that are bonded together at bond lines along the leading and trailing edges of the blade, improved methods for installing shear web inserts between the blade inserts and adjacent segments of the rotor blade are being developed. The pressure and suction shells are relatively lightweight and have structural properties (e.g., stiffness, bending resistance, and strength) that are not configured to withstand bending moments and other loads exerted on the rotor blade during operation. Thus, to increase the stiffness, bending resistance, and strength of the rotor blade, the body shell is typically reinforced with one or more structural members (e.g., opposing spar caps with shear web inserts configured therebetween) that join the inner and suction side surfaces of the shell halves.

However, such rotor blades are not without problems. One particular problem that arises relates to the connection of the shear clip and the shear web insert and clip in the rotor blade extension. Shear clips are typically used to reinforce the interface between the shear web and the spar cap, and are connected to both components at the shear web-spar cap interface. Because thermoset resins are generally used to form such rotor blades, thermoset-based joining techniques (such as applying a bonding paste or hand lay-up) must be used to secure the shear clips to the shear web inserts and spar caps. Accordingly, joining the shear clip and the shear web insert in the rotor blade may be difficult and time consuming. Furthermore, in many cases, the shear clips and shear web inserts may not be perfectly aligned with adjacent shear web and/or spar cap surfaces, thereby creating an offset or misalignment. These misalignments occur outside of manufacturing tolerances when connecting the shear web and spar caps. Thus, the resulting joint may not be optimal.

Accordingly, an improved method for connecting and repairing shear web inserts in wind turbine rotor blades including modular blades would be advantageous.

Disclosure of Invention

Aspects and advantages of the invention will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention.

In one aspect, a method for connecting and repairing shear webs includes the steps of: dry-fitting a shear web insert in the rotor blade assembly to establish a peripheral gap at an angled peripheral interface between the shear web insert and the rotor blade assembly, the angled peripheral interface being positioned between the shear web insert and at least one adjacent surface having a first shear web, a second shear web, a first side of the rotor blade assembly, and a second side of the rotor blade assembly; and then injecting a bonding paste into the peripheral gap.

In another aspect, a rotor blade assembly for a wind turbine is disclosed having a first side and a second side, wherein the first side of the rotor blade assembly corresponds to one of a pressure side or a suction side of a rotor and an opposite second side of the rotor blade assembly corresponds to the other of the pressure side or the suction side of the rotor blade assembly. The rotor blade assembly also has a first blade segment defining a joint end, the first blade segment including a first shear web having an angled interface at the joint end, and a second blade segment coupled to the joint end of the first blade segment, the second blade segment including a second shear web having an angled interface at the joint end.

At least one first connection device is coupled across at least a portion of the joint end, the at least one first connection device being at least partially coupled on a first side of at least one of the first and second shear webs. At least one second connection device is coupled across at least a portion of the joint end, the at least one second connection device being at least partially coupled on an opposite second side of at least one of the first and second shear webs. The bonding paste is injected into the angled interface.

In another aspect, an attachment apparatus is disclosed having at least one prefabricated clamp having horizontal and vertical portions, the horizontal portion of the at least one prefabricated clamp coupled to at least one of an inner surface of a first side of a rotor blade assembly and an inner surface of an opposing second side of the rotor blade assembly.

These and other features, aspects, and advantages of the present invention will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description, serve to explain the principles of the invention.

Drawings

A full and enabling disclosure of the present invention, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which:

FIG. 1 illustrates a perspective view of an embodiment of a wind turbine;

FIG. 2 illustrates a perspective view of an embodiment of one of the rotor blades of the wind turbine shown in FIG. 1;

FIG. 3 illustrates an exploded view of one embodiment of a rotor blade assembly in accordance with aspects of the present subject matter;

FIG. 4 illustrates a perspective view of one embodiment of a blade insert configuration that may be used with the disclosed rotor blade assembly in accordance with aspects of the present subject matter;

FIG. 5 illustrates a cross-sectional view of a portion of the blade insert shown in FIG. 4 taken along line 5-5;

FIG. 6 illustrates a perspective view of one embodiment of a blade segment configuration that may be used with the disclosed rotor blade assembly in accordance with aspects of the present subject matter;

FIG. 7 illustrates an exploded view of a portion of an embodiment of the disclosed rotor blade assembly, particularly illustrating a rotor blade assembly including the blade insert illustrated in FIGS. 4 and 5 and the blade segment illustrated in FIG. 6;

FIG. 8 shows a perspective assembled view of the components shown in FIG. 7;

FIG. 9 illustrates a cross-sectional view of a portion of the rotor blade assembly taken along line 9-9 of FIG. 8;

FIG. 10 illustrates a flow diagram of an embodiment of a method for installing a shear web insert within the rotor blade assembly illustrated in FIGS. 7-9;

FIG. 11 illustrates a side view of the rotor blade assembly illustrated in FIG. 9 taken along line 11-11;

FIG. 12 illustrates a top view of the rotor blade assembly illustrated in FIG. 9 taken along line 12-12;

FIG. 13 illustrates a side view of a shear web insert mounted horizontally in a rotor blade assembly;

FIG. 14 shows a side view of a shear web insert mounted against a locating device;

FIG. 15 shows a detail of a shear web insert having an angled peripheral interface forming a first gap and a second gap;

FIG. 16 shows a front view of the injection device position as it progresses around the angled peripheral interface of the shear web insert;

FIG. 17 shows a side view of the injection device position;

FIG. 18 shows a front view of a connection device having tapered plies;

FIG. 19 shows a top view of the first and second connection devices of FIG. 18 taken along line 19-19;

FIG. 20 shows a side view of the first and second connection devices mounted on opposite sides of the shear web insert.

Detailed Description

Reference now will be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, features illustrated or described as part of one embodiment, can be used with another embodiment to yield a still further embodiment. It is therefore intended that the present invention cover the modifications and variations of this invention provided they come within the scope of the appended claims and their equivalents.

In general, the present subject matter relates to methods and apparatus for installing a horizontal shear web insert between a blade segment and a blade insert of a rotor blade assembly. The methods described herein are not limited to blade inserts only, but may be used in any blade joint involving a shear web, for example in assembling a modular blade. In particular, in several embodiments, the blade segments and blade inserts may each include a shear web extending longitudinally therein. Due to the configuration of the blade inserts and/or blade segments, gaps may be defined between the shear webs of such components. As a result, the shear web inserts must be installed across the gap defined between the blade shear webs. As will be described below, in several embodiments, the blade insert may include an elongate protrusion extending into the blade segment in substantial alignment with one of the spar caps thereof, thereby preventing the shear web insert from being vertically mounted between the shear webs. Thus, according to aspects of the present subject matter, the disclosed method may be used to mount a shear web insert horizontally between shear webs.

Installation of horizontal shear webs can be difficult and confusing. The injection method and apparatus disclosed herein allow the shear web to be positioned in a horizontal manner without the use of a bonding paste to maintain position, but instead using spacers. Once positioned, a bonding paste is then injected into the peripheral gap to complete the joint. The shear web insert may be tapered to form an angled interface cut around the interface to allow for proper flow of the bond paste. Without a properly angled interface, the bond paste would not flow properly to the other side (if the gap is too small) or allow too much bond paste to flow to the other side (if the gap is too large). The installation methods and apparatus of the horizontal shear web insert disclosed herein may use at least one connection apparatus, such as a two-piece c-clip, at the joint between the blade shear web and the shear web insert as a shear clip. Previously, this was done by laminating the joints with a separate pre-cure cycle step between them. The two-piece c-clip connection or shear clip disclosed herein allows for the installation of a pre-made c-clip without a pre-curing step and without the need for additional grinding and preparation prior to installation. The two-piece c-clip may overlap, allowing the typical size of c-clip to be installed in blades having different sizes due to tolerances, without the need for pre-sizing in advance. The c-clip may also be tapered in multiple regions to reduce stress concentrations. The injection method and apparatus disclosed herein can eliminate pre-cure cycles, reduce cycle time, reduce mess, and provide better joints while eliminating previous paste application problems.

Referring now to the drawings, FIG. 1 illustrates a perspective view of an embodiment of a wind turbine 10. As shown, wind turbine 10 generally includes a tower 12 extending from a support surface 14, a nacelle 16 mounted on tower 12, and a rotor 18 coupled to nacelle 16. Rotor 18 includes a rotatable hub 20 and at least one rotor blade 22 coupled to hub 20 and extending outwardly from hub 20. For example, in the illustrated embodiment, the rotor 18 includes three rotor blades 22. However, in alternative embodiments, rotor 18 may include more or less than three rotor blades 22. Each rotor blade 22 may be spaced about hub 20 to facilitate rotating rotor 18 to enable kinetic energy to be transferred from the wind into usable mechanical energy, and subsequently, electrical energy. For example, hub 20 may be rotatably coupled to an electrical generator (not shown) positioned within nacelle 16 to allow electrical energy to be generated.

Referring now to FIG. 2, a perspective view of one of the rotor blades 22 illustrated in FIG. 1 is shown. As shown, the rotor blade 22 generally includes a blade root 24 configured for mounting the rotor blade 22 to the hub 20 of the wind turbine 10 (FIG. 1) and a blade tip 26 disposed opposite the blade root 24. The body 28 of the rotor blade 22 may generally be configured to extend between the blade root 24 and the blade tip 26, and may serve as a shell/skin for the blade 22. In several embodiments, the body 28 may define a substantially aerodynamic profile, such as by defining a symmetrical or curved airfoil-shaped cross-section. As such, the body 28 may include a suction side 32 and a pressure side 30 extending between a leading edge 34 and a trailing edge 36. Further, the rotor blade 22 may have a span 38 defining the overall length between the blade root 22 and the blade tip 24 and a chord 40 defining the overall length between the leading edge 34 and the trailing edge 36. As generally understood, the chord 40 may vary in length with respect to the span 38 as the rotor blade 22 extends from the blade root 22 to the blade tip 24.

In several embodiments, the body 28 of the rotor blade 22 may be formed as a single, unitary member. Alternatively, the body 28 may be formed from a plurality of shell members. For example, the body 28 may be fabricated from a first shell half that generally defines a pressure side 30 of the rotor blade 22 and a second shell half that generally defines a suction side 32 of the rotor blade 20, wherein the shell halves are secured to one another at a leading edge 34 and a trailing edge 36 of the blade 22. Additionally, the body 28 may generally be formed of any suitable material. For example, in one embodiment, the body 28 may be formed entirely of a ply composite material, such as a carbon fiber reinforced ply composite or a glass fiber reinforced ply composite. Alternatively, one or more portions of the body 28 may be configured in a laminate configuration and may include a core 42 formed of a lightweight material, such as wood (e.g., balsa wood), foam (e.g., extruded polystyrene foam), or a combination of such materials, disposed between the ply composite material layers (e.g., as shown in fig. 6).

It should be appreciated that the rotor blade 22 may also include one or more longitudinally extending structural members configured to provide increased stiffness, bending resistance, and/or strength to the rotor blade 22. For example, in several embodiments, the rotor blade 22 may include a pair of spar caps (e.g., a top spar cap 44 and a bottom spar cap 46) and one or

more shear webs

48, 146 extending between the opposing spar caps 44, 46 (e.g., as shown in FIG. 6).

Referring now to FIG. 3, one embodiment of a rotor blade assembly 100 is illustrated, in accordance with aspects of the present subject matter. As illustrated, the rotor blade assembly 100 may include a first blade segment 102, a second blade segment 104, and a second blade segment 106 configured to be coupled between the first blade segment 102 and the second blade segment 104. Generally, the rotor blade assembly 100 may be configured such that a complete rotor blade is formed when the first and

second blade segments

102, 104 are coupled together via the blade insert 106.

In several embodiments, the first and

second blade segments

102, 104 may be formed by dividing a pre-existing rotor blade 22 into two separate blade segments. For example, as shown in FIG. 2, in one embodiment, the illustrated rotor blade 22 may be divided into a first blade segment 102 and a second blade segment 104 by cutting the rotor blade 22 along a joint or cut line 108. Thus, in the illustrated embodiment, the first blade segment 102 may correspond to a root segment of the rotor blade 22 and may extend between a first joint end 110 formed at the cut line 108 and the blade root 24. Similarly, in the illustrated embodiment, the second blade segment 104 may correspond to a tip segment of the rotor blade 22 and may extend between a second joint end 112 formed at the cut line 108 and the blade tip 26.

It should be appreciated that, although the first blade segment 102 is illustrated as a root segment and the second blade segment 104 is illustrated as a tip segment, the terms "first blade segment" and "second blade segment" may generally refer to any suitable segment or section of the rotor blade 22. For example, in another embodiment, the first blade segment 102 may correspond to a tip segment of the rotor blade 22 and the second blade segment 104 may correspond to a root segment of the rotor blade 22. In further embodiments, the first and

second blade segments

102, 104 may correspond to shorter segments of the rotor blade 22.

Further, it should be appreciated that the terms "first blade segment" and "second blade segment," as used herein, need not be limited to a single continuous blade segment. For example, in the illustrated embodiment, the first blade segment 102 may be formed from a single unitary blade segment extending between the blade root 24 and the first joint end 110, or the first blade segment 102 may be formed from two or more blade segments extending between the blade root 24 and the first joint end 110 when coupled together. Similarly, in the illustrated embodiment, the second blade segment 104 may be formed from a single unitary blade segment extending between the second joint end 112 and the blade tip 26, or the second blade segment 104 may be formed from two or more blade segments extending between the second joint end 112 and the blade tip 26 when coupled together.

Moreover, it should be appreciated that the cut line 108 (FIG. 2) may generally be located at any suitable location along the span 38 of the rotor blade 22. For example, in one embodiment, the cut line 108 may be a distance from the blade root 24 in a range of about 40% to about 95% of the span 38, such as about 40% to about 80% of the span 28 or about 50% to about 65% of the span 38. However, it is contemplated that in other embodiments, the cut line 108 may be less than 40% of the span 38 or greater than 95% of the span 38 from the blade root 34.

It should also be appreciated that, in alternative embodiments, the first and

second blade segments

102, 104 need not be formed by cutting or otherwise separating the pre-existing rotor blade 22 into two separate blade segments. For example, in another embodiment, the first and

second blade segments

102, 104 may be individually manufactured as modular blades and assembled along with the blade insert 106 to form the disclosed rotor blade assembly 100.

Still referring to FIG. 3, the blade insert 106 of the rotor blade assembly 100 may generally include an elongated aerodynamic body 114 extending between a forward end 116 and an aft end 118, thereby forming individual blade segments of the rotor blade assembly 100. Generally, the blade insert 106 may be configured to be coupled between the first and

second blade segments

102, 104 so as to form the rotor blade assembly 100. In particular, a leading end 116 of the blade insert 106 may be configured to be coupled to the joint end 110 of the first blade segment 102, and a trailing end 118 of the blade insert 106 may be configured to be coupled to the joint end 112 of the second blade segment 104. Suitable configurations and methods for attaching the blade insert 106 between the first and

second blade segments

102, 104 are generally described below with reference to FIGS. 4-9.

4-6, one embodiment of a particular blade insert/segment configuration that may be utilized to effectively and efficiently secure a blade insert 106 between a first blade segment 102 and a second blade segment 104 of a rotor blade assembly 100 is illustrated in accordance with aspects of the present subject matter. In particular, FIG. 4 illustrates a perspective view of the blade insert 106, and FIG. 5 illustrates a partial cross-sectional view of the blade insert 106 shown in FIG. 4 taken along line 5-5. Additionally, FIG. 6 illustrates a perspective view of a corresponding configuration that may be used with the first blade segment 102 and/or the second blade segment 104.

As indicated above, the blade insert 106 may generally include an elongated body 114 extending between a forward end 116 and an aft end 118, wherein the forward end 116 is configured to be coupled to the joint end 110 of the first blade segment 102 and the aft end 118 is configured to be coupled to the joint end 112 of the second blade segment 104. In general, the body 114 may be configured to define a substantially aerodynamic profile, such as by defining a symmetrical or curved airfoil-shaped cross-section. Thus, as shown in fig. 4 and 5, the body 114 may include a top side 120 (e.g., a pressure side) and a bottom side 122 (e.g., a suction side) extending between a leading edge 124 and a trailing edge 126. Additionally, as shown, the top side 120 of the body 114 may be configured to span between a leading edge 128 disposed at the leading end 116 of the blade insert 106 and a trailing edge 130 disposed at the trailing end 118 of the blade insert 106. Similarly, the bottom side 122 of the body 114 may be configured to extend spanwise between a leading edge 132 disposed at the leading end 116 of the blade insert 106 and a trailing edge 134 disposed at the trailing end 118 of the blade insert 106.

The blade insert 106 may also include internal structural components that are the same as or similar to the first and

second blade segments

102, 104. For example, as shown in fig. 4, the blade insert 106 may include a pair of longitudinally extending spar caps (e.g., a top spar cap 142 and a bottom spar cap 144), wherein each

spar cap

142, 144 is integrated into and/or forms a portion of the top side 120 or the bottom side 122 of the blade insert 106. Additionally, the blade insert 106 may include one or more shear webs 146 (FIG. 5) extending between the opposing spar caps 142, 144.

Additionally, in several embodiments, a portion of the top side 120 of the blade insert 106 may be recessed or offset from the leading edge 132 and the trailing edge 134 of the bottom side 122 of the blade insert 106. For example, as shown in FIG. 4, portions of top side 120 may be offset inwardly from leading edge 132 of bottom side 122 by a first spanwise distance 136 along either side of top spar cap 142, thereby defining separate offset portions of leading edge 128 of top side 120. Similarly, portions of the top side 120 may also be offset inwardly from the trailing edge 134 of the bottom side 122 by a second spanwise distance 138 along either side of the bottom spar cap 142, thereby defining separate offset portions of the trailing edge 130 of the top side 120. As will be described below, by offsetting portions of the top side 120 (as shown in FIG. 4), separate access windows 140, 141 (see FIG. 7) may be defined at each

end

116, 118 of the blade insert 106 when the insert 106 is positioned between the first and

second blade segments

102, 104.

Such access windows

140, 141 may generally allow service personnel to access the interior of the rotor blade assembly 100, allowing various components to be positioned within the assembly 100 to facilitate securing the blade insert 106 between the

blade segments

102, 104. For example, as will be described below, the shear web insert 183 may be inserted through one of the

access windows

140, 141 and horizontally mounted between the blade insert 106 and the

blade segments

102, 104 to couple the shear web of the

blade segments

102, 104 to the shear web insert 183 of the blade insert 106.

It should be appreciated that the first spanwise distance 136 and the second spanwise distance 138 may generally correspond to any suitable distance. Additionally, in one embodiment, the first spanwise distance 136 may be equal to the second spanwise distance 138. Alternatively, the first spanwise distance 136 may be greater than or less than the second spanwise distance 138.

It should also be appreciated that the terms "forward" and "aft" as used herein are used merely to distinguish between the opposite ends 110, 112 and/or

edges

128, 130, 132, 134 of the blade insert 106. Thus, although the leading end 110 of the blade insert 106 is described herein as being configured to be coupled to the joint end 110 of the first blade segment 102, the trailing end 112 of the blade insert 106 may instead be configured to be coupled to the first blade segment 102. Similarly, as used herein, the terms "top" and "bottom" are used merely to distinguish the

opposite sides

120, 122 of the blade insert 106. For example, in the illustrated embodiment, the top side 120 of the blade insert 106 corresponds to the pressure side and the bottom side 122 corresponds to the suction side. However, in another embodiment, the top side 120 of the blade insert 106 may correspond to the suction side and the bottom side 122 may correspond to the pressure side.

Additionally, in several embodiments, a portion of the top side 120 of the blade insert 106 may also be configured to extend beyond the leading edge 132 and the trailing edge 134 of the bottom side 122 of the blade insert 106. In particular, as shown in fig. 4 and 5, an elongated portion 147 of the top side 120 (generally aligned with the top spar cap 142) may extend beyond the leading edge 132 and the trailing edge 134 of the bottom side 122, thereby defining an extension in the leading edge 128 and the trailing edge 130 of the top side 120. As will be described below, such an elongated portion 147 of the top side 120 may be configured to extend to a position at and/or adjacent to the

joint end

110, 112 of the

blade segment

102, 104 when the blade insert 106 is positioned between the

blade segments

102, 104.

Moreover, in several embodiments, one or more tapered or scarf sections may be defined along the top side 120 and the bottom side 122 of the vane insert 106. For example, as shown in fig. 4, a first top scarf section 152 and a second top scarf section 154 may be defined along the outer surface of the top side 120, where the first top scarf section 152 extends from the inner edge 156 to the leading edge 128 of the elongated portion 147 of the top side 120, and the second top scarf section 254 extends from the inner edge 158 to the trailing edge 130 of the elongated portion 147 of the top side 120. Similarly, as shown in fig. 4, a first bottom scarf section 160 and a second bottom scarf section 162 may be defined along the inner surface of bottom side 122, with first bottom scarf section 160 extending from an inner edge 164 to leading edge 132 of bottom side 122, and second top scarf section 162 extending from an inner edge (not shown) to trailing edge 134 of bottom side 122. In such embodiments, each

scarf section

152, 154, 160, 162 may be configured to taper outwardly from its

inner edge

156, 158, 164 (i.e., wherein the height of each

scarf section

152, 154, 160, 162 increases from its

inner edge

156, 158, 164 to the respective leading 128, 132 or trailing 130, 134 edges of the top and

bottom sides

120, 122 of the vane insert 106).

It should be appreciated that the

scarf sections

152, 154, 160, 162 may generally be defined at any suitable chordwise location along the top and

bottom sides

120, 122 of the blade insert 106. However, in several embodiments, the

scarf segments

152, 154, 160, 162 may be aligned with the spar caps 142, 144 of the blade insert 106. For example, as shown in fig. 4, the

top scarf sections

152, 154 are generally aligned with the top spar cap 142, while the

bottom scarf sections

160, 162 are generally aligned with the bottom spar cap 144. In such embodiments, a width 168 (fig. 4) of each

scarf section

152, 154, 160, 162 may generally correspond to a width of the spar caps 142, 144. Alternatively, the width 168 of each

scarf section

152, 154, 160, 162 may be greater than or less than the width of the spar caps 142, 144.

Also, a portion of the shell forming the blade insert 106 may be recessed relative to the leading and trailing

edges

128, 132, 130, 134 of the top and

bottom sides

120, 122. For example, as shown in fig. 4, only the inner layer (e.g., one or more layers of laminated composite material) of the top side shell may extend to the leading edge 128 and the trailing edge 130 of the top side 120, while only the outer layer (e.g., one or more layers of laminated composite material) of the bottom side shell may extend to the leading edge 132 and the trailing edge 134 of the bottom side 122, thereby defining a top flange 172 and a bottom flange 174 that extend across portions of

such edges

128, 130, 132, 134. As will be described below, the top and

bottom flanges

172, 174 may facilitate securing the blade insert 106 between the first and

second blade segments

102, 104. Outer layers of the shell (e.g., one or more outer layers of laminated composite material and/or 42 of one or more layers of core material) may then be positioned on the

flanges

172, 174 to create a smooth surface along the inner and outer surfaces of the rotor blade assembly 100.

Referring now to FIG. 6, a perspective view of a suitable segment configuration for attaching each

blade segment

102, 104 to the blade insert 106 shown in FIGS. 4 and 5 is shown, in accordance with aspects of the present subject matter. In particular, FIG. 6 illustrates a perspective view of the joint end 110 of the first blade segment 102. However, it should be appreciated that the joint end 112 of the second blade segment 104 may be configured the same as or similar to the joint end 110 illustrated in FIG. 6.

As shown, the blade segment 102 may be modified to include

scarf sections

175, 176 configured to align with the

scarf sections

152, 160 of the blade insert 106. In particular, in the illustrated embodiment, the blade segment 102 includes a top scarf section 175 defined along an outer surface of the pressure side 30 thereof, the top scarf section 175 configured to align with the top scarf section 152 defined at the leading edge 128 of the top side 120 of the blade insert 106. Similarly, the blade segment 102 includes a bottom scarf section 176 defined along the inner surface of the suction side 32 thereof, the bottom scarf section 176 being configured to align with the bottom scarf section 160 defined at the leading edge 132 of the bottom side 122 of the blade insert 106. As will be described below, a scarf connector may be positioned across each aligned pair of

scarf sections

152, 160, 175, 176 to provide a means for securing the blade segment 102 to the blade insert 106.

Further, similar to the blade insert 106, the blade segment 102 may include an offset edge 177 at the joint end 110 thereof that is offset from an edge of the opposite side of the blade segment 102 by a given spanwise distance 178. In particular, in the illustrated embodiment, a portion of the shell forming the pressure side 30 may be removed between the joint end 110 of the blade segment 102 and the leading edge of the top scarf section 175, thereby defining an offset edge 177. As will be described below, when such components are positioned adjacent to one another, this removed portion of the shell may form part of the

access windows

140, 141 defined between the blade segment 102 and the blade insert 106.

Moreover, as shown in FIG. 6, a portion of the shell forming the pressure and

suction sides

30, 32 of the blade segment 102 may be recessed relative to the joint end 110 of the blade segment 102. For example, similar to the blade insert 106, only the inner layer of the shell (e.g., one or more layers of laminated composite material) may be configured to extend to the joint end 110 of the blade segment 102, thereby defining a top flange 179 and a bottom flange 180 around the perimeter portion of the joint end 110.

Referring now to fig. 7-9, a partial assembled view of the blade insert 106 shown in fig. 4 and 5 and the blade segment 102 shown in fig. 6 is illustrated, in accordance with an aspect of the present invention. In particular, FIG. 7 illustrates a perspective view of the blade insert 106 and the blade segment 102 positioned end-to-end with suitable components for securing the blade insert 106 to the blade segment 102 exploded outward. FIG. 8 illustrates a perspective assembly view of the various components shown in FIG. 7, and FIG. 9 illustrates a cross-sectional view of the assembly shown in FIG. 8 taken along line 9-9.

As shown in fig. 7, when the blade segment 102 and the blade insert 106 are positioned end-to-end, separate access windows (e.g., the first access window 140 and the second access window 141) may be defined between such components along either side of the elongated portion 147 of the top side 120 of the blade insert 106.

Such access windows

140, 141 may generally allow service personnel access to the interior of the rotor blade assembly 100, thereby facilitating installation of many of the assembly components shown in FIG. 7. For example, in one embodiment, the bottom snap connector 181, the bottom shell insert 182, and the shear web insert 183 may be mounted within the rotor blade assembly 100 via the passageways provided through the

access windows

140, 141. Thereafter, the

access windows

140, 141 may be covered by

suitable window coverings

184a, 184b to allow the assembly process to be completed.

As indicated above, when positioning the blade insert 106 and the blade segment 102 end-to-end, the bottom scarf section 160 at the leading end 116 of the blade insert 106 may be configured to align with the bottom scarf section 176 of the blade segment 102. In particular, as shown in fig. 9, the aligned

bottom scarf sections

160, 176 may be configured to abut each other when the blade insert 106 and the blade segment 102 are positioned together. In such embodiments, a bottom scarf connector 181 may be positioned across the

bottom scarf sections

160, 176 to facilitate coupling the blade insert 106 to the blade segment 102. In particular, as shown in fig. 7 and 9, the bottom scarf connector 181 may generally define a tapered profile that corresponds to the tapered profile defined by the

bottom scarf sections

160, 176. Thus, as shown in fig. 9, the bottom scarf connector 181 may be configured to extend across the interface defined between the blade segment 102 and the blade insert 106 so as to fill the open area defined by the

bottom scarf sections

160, 176.

In several embodiments, the bottom scarf connector 181 may comprise a prefabricated component configured to be installed separately within the rotor blade assembly 100 (via one of the access windows 140, 141) and secured across the aligned

bottom scarf sections

160, 176, such as by securing the scarf connector 181 within the

bottom scarf parts

160, 176 using a suitable bonding paste (such as a bonding paste) and/or mechanical fasteners (e.g., bolts, screws, pins, rivets, brackets, and/or the like). Alternatively, the bottom scarf connector 181 may be formed or otherwise established within the aligned

bottom scarf sections

160, 176. For example, in one embodiment, the scarf connector 181 may be formed using a wet lay-up process, wherein a plurality of plies (including reinforcing materials such as glass or carbon fibers) are positioned across and/or within the

bottom scarf sections

160, 176, and a resin or other suitable matrix material is rolled or otherwise applied over the surfaces of the plies and cured.

In addition to the

bottom scarf sections

160, 176, the

bottom flanges

174, 180 of the blade insert 106 and the blade segment 102 may also be configured to abut each other when the blade insert 106 and the blade segment 102 are positioned end-to-end. Thus, suitable bottom shell inserts 182 may be secured across the

bottom flanges

174, 180 along either side of the bottom snap connector 181 to further secure the blade insert 106 and the blade segment 102 to one another. In particular, the bottom shell insert 182 may generally be configured to extend across the interface defined between the blade segment 102 and the blade insert 106 so as to fill the open area defined by the

bottom flanges

174, 180. For example, as shown in fig. 7, the bottom shell insert 182 may generally define a profile that matches the profile of the corresponding portions of the shells of the blade insert 106 and the blade segment 102, and may also be formed from the same material (e.g., one or more layers of laminate members and/or one or more layers of core material 44). It should be appreciated that similar to the bottom snap connector 181, the bottom shell insert 182 may be a pre-fabricated component or may be formed or otherwise configured within the open area defined by the

bottom flanges

174, 180.

As indicated above, the shear web insert 183 may also be mounted within the rotor blade assembly 100 via one of the

access windows

140, 141. As shown in fig. 7, the shear web insert 183 may generally include a first side 302 and a second side 304 extending between a first end 306 and a second end 308. In general, the shear web insert 183 may be configured to extend spanwise between the blade segment 102 and the ends of the

shear webs

48, 146 of the blade insert 106. In particular, as shown in fig. 9, the shear web insert 183 may be configured to define a length 185 between its first and second ends 306, 308, the length 185 generally corresponding to a gap defined between the ends of the first and

second shear webs

48, 146 of the

blade segments

102, 106. Thus, the shear web insert 183 may be inserted into the rotor blade assembly 100 via one of the

access windows

140, 141 and subsequently secured between the

shear webs

48, 146. For example, as will be described below, one or more

positioning device segments

310, 312, 315 and/or one or more connection devices (fig. 9) may be coupled along the

inner surfaces

316, 318 of the first and

second sides

317, 319 of the rotor blade assembly 100 (e.g., the inner surface 316 (fig. 11) defined along the pressure or first side 317 and the inner surface 318 (fig. 11) defined along the suction or second side 319 of the assembly 100) to facilitate installation of the shear web insert 183 between the

shear webs

48, 146.

After such components are installed within the rotor blade assembly 100, a

suitable window shroud

184a, 184b may then be installed between the blade insert 106 and the blade segment 106 so as to cover at least a portion of each

access window

140, 141. For example, as shown in fig. 7, the first window cover 184a may be configured to extend across and/or cover at least a portion of the first access window 140. Similarly, the second window cover 184b may be configured to span and/or cover at least a portion of the second access window 141. As shown in fig. 7, the

window coverings

184a, 184b may generally have a similar configuration as the shells used to form the blade insert 106 and the blade segment 102. For example, the

window coverings

184a, 184b may be formed from a laminate construction including one or more layers of laminate material and one or more layers of core material 42.

Additionally, similar to the blade insert 106 and the blade segment 102, a portion of the shell forming the

window coverings

184a, 184b may be recessed or offset, thereby defining a cover flange 188 around the edges of the

window coverings

184a, 184 b. Thus, when each window cover 184a, 214b is installed across its corresponding

access window

140, 141, the cover flange 188 may be configured to abut the blade insert 106 and the

top flanges

172, 179 of the blade segment 102. Thereafter, a suitable top shell insert 189 may be secured across each interface defined between the blade segment 212 and the

window cover

184a, 184b and across each interface defined between the blade insert 106 and the

window cover

184a, 184b so as to fill the open area defined by the top and cover

flanges

172, 179, 188. For example, as shown in FIG. 7, the top shell insert 189 may generally define a profile that matches the profile of corresponding portions of the shells of the blade insert 106 and the blade segment 212, and may also be formed from the same material (e.g., one or more layers of laminate members and/or one or more layers of core material 42).

Moreover, as shown in the illustrated embodiment, the rotor blade assembly 100 may further include a top scarf connector 190, the top scarf connector 190 being configured to be positioned across the aligned

top scarf segments

152, 175 of the blade insert 106 and the blade segment 102. As shown in fig. 7, the top-scarf connector 190 may define a tapered profile that corresponds to the tapered profile defined by the top-scarf sections 151, 175. Thus, as particularly shown in fig. 9, the top scarf connector 190 may be configured to extend across the interface defined between the blade segment 102 and the blade insert 106 so as to fill the area defined by the aligned

top scarf sections

152, 175.

It should be appreciated that similar to the bottom snap connector 181 and the bottom shell insert 182, the top snap connector 190 and the tip shell insert 189 may be prefabricated components, or may be formed or otherwise constructed during assembly of the rotor blade assembly 100.

It should also be appreciated that after the various components of the rotor blade assembly 100 are assembled between the blade segment 102 and the blade insert 106, a laminate ply may be applied around the outer surface of the assembly 100 to ensure a smooth aerodynamic transition between the blade segment 102 and the blade insert 106. For example, a wet lay-up process may be used to apply a lay-up ply, wherein one or more plies (including reinforcing materials such as glass or carbon fibers) are positioned along the outer surface, and a resin or other suitable material is rolled up or otherwise applied onto the surface of the plies to form a smooth profile.

Moreover, it should be appreciated that although the blade insert 106 is described with reference to FIGS. 7-9 as being simply secured to one of the blade segments (e.g., the first blade segment 102), the same or similar methods and the same or similar components may be used to secure the blade insert 106 to the other blade segment (e.g., the second blade segment 104). For example, a bottom mating connector 181, a bottom shell insert 182, a shear web insert 183, a window covering 184a, 184b, a top shell insert 189, and a top mating connector 190 may be mounted between the aft end 118 of the blade insert 106 and the joint end 112 of the second blade segment 104 to allow such components to be secured to one another in the same manner that the blade insert 106 and the first blade segment 102 are secured together (e.g., as shown in FIGS. 7-9).

Further, it should be appreciated that the blade inserts 106 described herein may be considered blade segments. Accordingly, one of ordinary skill in the art will appreciate that the disclosed rotor blade assembly 100 may include one or more blade inserts 206, wherein each blade insert forms a single segment of the rotor blade assembly 100.

Referring now to FIG. 10, a flow diagram of an embodiment of a method 200 for installing a shear web insert 183 between a blade insert 106 and one of the

blade segments

102, 104 is depicted in accordance with aspects of the present subject matter. Generally, due to the configuration of the blade insert 106 (i.e., due to the elongated portion 147), the shear web insert 183 must be installed horizontally. In particular, the shear web 183 must be inserted through one of the

access windows

140, 141 and then horizontally between the second shear web 146 for the blade insert 106 and the first shear web 48 for the

corresponding blade segment

102, 104.

It should be appreciated that the method 200 will generally be described herein with reference to installing the shear web insert 183 between the blade insert 106 and the first blade segment 102. However, the same method may also be used for installing a shear web insert 183 between the blade insert 106 and the second blade segment 102 or for assembling a modular blade having a first shear web 48 and a second shear web 146. To describe the disclosed method 200, the shear web 48 of the first blade segment 102 is referred to as a "first shear web 48" and the shear web 146 of the blade insert 106 is referred to as a "second shear web 146". Thus, the shear web inserts 183 may be provided at both ends of the blade insert 106, i.e., at both joints of the blade insert 106. It should also be appreciated that, although the method elements are presented in a particular order, the elements may generally be performed in any suitable order consistent with the disclosure provided herein.

As shown in fig. 10, a method 200 for connecting a blade segment 102 and a blade insert 106 of a rotor blade assembly 100 at a shear web joint is disclosed, the blade segment 102 including a first shear web 48 and the blade insert 106 including a second shear web 146. Method steps 202-204 include dry-assembling the shear web insert 183 in the rotor blade assembly 100 to establish a peripheral gap 331 at an angled peripheral interface 300 between the shear web insert 183 and the rotor blade assembly 100, the angled peripheral interface 300 being positioned between the shear web insert 183 and at least one adjacent surface of the first shear web 48, the second shear web 146, the first side of the rotor blade assembly 317, and the second side of the rotor blade assembly 319. Bond paste 328 is then injected into perimeter gap 331.

Additional method steps may include: coupling at least one first connection device (342) across a portion of the perimeter gap 331, the at least one first connection device 342 being disposed partially on the first side 302 of at least one of the first and

second shear webs

48, 146; and then coupling at least one second connection device 344 across a portion of the perimeter gap 331, the at least one second connection device 344 being disposed in part on the opposing second side 304 of at least one of the first and

second shear webs

48, 146.

Further, the method may include coupling the at least one first and second

positioning device segments

310, 312 along an

inner surface

316, 318 of at least one of the first side 317 or the second side 319 of the rotor blade assembly 100. A plurality of spacers 315 are then placed along at least one of the bottom surface 332, the first end 306, or the second end 308 of the shear web insert 183, the plurality of spacers 315 being aligned with the first side surface 302 of the shear web insert 183. The shear web insert 183 is then positioned between the first and

second shear webs

48, 146 until the first side 302 of the shear web insert 183 engages the first and

second locator segments

310, 312. The spacers 315 will thus define a perimeter gap 331 around the angled perimeter interface 300 of the shear web insert 183. The bond paste is then injected into the perimeter gap 331 around the angled perimeter interface 300 of the shear web insert 183.

In general, the

positioning device segments

310, 312 may have any suitable configuration that allows

such devices

310, 312 to function as a mechanical stop for positioning the shear web insert 183 between the first and

second shear webs

48, 146. As shown, in several embodiments, the

positioning device segments

310, 312 may each define an "L" shaped structural segment having a horizontal portion 322 coupled to the

inner surfaces

316, 318 of the assembly 100 (e.g., using a suitable adhesive paste or mechanical fastener) and a vertical portion 324 extending generally perpendicularly from the horizontal portion 322. In such embodiments, the vertical portion 324 of each

positioning device segment

310, 312 may generally be configured to act as a mechanical stop for the shear web insert 183 when the shear web insert 183 is inserted between the first and

second shear webs

48, 146. In other embodiments, the

positioning device segments

310, 312 may have any other suitable configuration that allows such devices to function as described herein.

In addition, as shown in FIGS. 9-13, the first and

second positioner segments

310, 312 may generally be configured to be aligned with each other in a horizontal or chordwise direction of the rotor blade assembly 100 (i.e., indicated by arrow 320). In particular, in several embodiments, the vertical portions 324 of the

positioning device segments

310, 312 may be aligned at a first chordwise location (indicated by line 326 in fig. 13) that generally corresponds to a location at which the first side 302 of the shear web insert 183 is positioned when the insert 183 is properly installed between the first and

second shear webs

48, 146.

Moreover, in several embodiments, the locating

device segments

310, 312 may be individually placed spanwise (indicated by arrow 326 in fig. 13) along all or a majority of the length 185 of the shear web insert 183. For example, as shown in fig. 9, the

positioning device segments

310, 312 may be individually placed along a length generally corresponding to the length 185 of the shear web insert 183. Alternatively, the

positioning device segments

310, 312 may be placed separately to define a length that is shorter than the overall length 185 of the shear web insert 183. In such embodiments, the plurality of

positioning device segments

310, 312 may be spaced apart, for example, along the length 185 of the shear web insert 183.

It should be appreciated that in addition to functioning as a mechanical stop, the

positioning device segments

310, 312 may also function as a means for transferring loads through the rotor blade assembly 100. For example, by coupling one or more

positioning device segments

310, 312 along the length 185 of the shear web insert 183, loads may be transferred between the shear web insert 183 and the body 114 of the blade insert 106 and/or the body 28 of the blade segment 102.

Referring back to FIG. 10, at (208), the method 200 includes injecting a bond paste 328 into the perimeter gap 331 around the angled perimeter interface 300 of the shear web insert 182 of the rotor blade assembly 100 at a location adjacent to the

positioning device segments

310, 312. The injection of the bonding paste may be performed by an injection device 366 such as a 'tip' or injector nozzle. When injecting the bonding paste 328, an amount of the bonding paste 328 may be injected in a manner such that the bonding paste 328 extends outwardly from the vertical portion 324 of the positioning device segment 310, 412 along the

inner surface

316, 318. Upon injection of the bond paste 328 along the

inner surfaces

316, 318, it may be desirable to provide a sufficient amount of bond paste 328 such that extrusion or flash-out occurs at the interface between the

positioning device segments

310, 312 and the shear web insert 183, and the interface between the

inner surfaces

316, 318 and the shear web insert 183 when the insert 183 is positioned between the first and second shear webs 48, 146 (e.g., as shown in fig. 14). Thus, the bond paste 328 may be evenly dispersed between the shear web insert 183 and the

positioning device segments

310, 312 and between the shear web insert 183 and the

inner surfaces

316, 318 of the rotor blade assembly 100.

It should be appreciated that any suitable bond paste 328 known in the art may be used to secure the shear web insert 183 between the first and

second shear webs

48, 146. Additionally, it should be appreciated that the bond paste 328 may be injected along the

inner surfaces

316, 318 of the rotor blade assembly 100 to form any suitable cross-sectional shape.

Referring back to fig. 10, at 206, the method 200 includes positioning the shear web insert 183 between the first shear web 48 and the second shear web 146. In particular, in several embodiments, the shear web insert 183 may be inserted between the first and

second shear webs

48, 146 until the first side 320 of the insert 183 engages the

positioning device segments

310, 312, thereby indicating that the shear web insert 183 is properly positioned within the rotor blade assembly 100. As used herein, the shear web insert 183 may be engaged with the

positioning device segments

310, 312 by

direct contact devices

310, 312 or by indirect contact devices 310, 312 (e.g., via a bond paste 328). For example, as shown in fig. 14, the shear web insert 183 may be considered to engage with the

positioning device segments

310, 312 even if there is a layer of bond paste 328 between the first side face 302 of the shear web insert 183 and the vertical portion 324 of each

positioning device segment

310, 312.

As shown in fig. 14, when the shear web insert 183 is pushed horizontally into engagement with the

positioning device segments

310, 312, the bonding paste 328 may squeeze out or spill out from between the shear web insert 183, the

inner surfaces

316, 318, and the

positioning device segments

310, 312, providing an indication that the bonding paste 328 has spread between such components. In several embodiments, the top surface 330 and/or the bottom surface 332 of the shear web insert 182 may be shaped or otherwise configured to help allow the bond paste 183 to be properly extruded. For example, as particularly shown in the close-up view of FIG. 14, the top and

bottom surfaces

330, 332 may be angled relative to the

inner surfaces

316, 318 of the rotor blade assembly 100. In particular, the top and

bottom surfaces

330, 332 and the first and second ends 306, 308 may include a perimeter gap 331 positioned about the angled perimeter interface 300, and may be angled with respect to the

positioning device segments

310, 312 such that a first gap 334 defined between the top and

bottom surfaces

330, 332 and the

inner surfaces

316, 318 at the first side 302 of the shear web insert 183 is less than a second gap 336 defined between the top and

bottom surfaces

330, 332 and the

inner surfaces

316, 318 at the second side 304 of the shear web insert 183. For example, in several embodiments, the top surface 330 and the bottom surface 332 may be configured to define an angle 338 relative to the

inner surfaces

316, 318, the angle 338 being in a range of about 5 degrees to about 50 degrees (such as about 10 degrees to about 45 degrees or about 10 degrees to about 25 degrees and any other subranges therebetween). By configuring the top and

bottom surfaces

330, 332 as shown in fig. 12 and 13, the bond paste 328 may advantageously be spread between the shear web insert 182 and the inner surface/

positioning device segments

316, 318, 310, 312 when the shear web is properly positioned between the first and

second shear webs

48, 146.

It should be appreciated that the

gaps

334, 336 defined between the shear web insert 183 and the

inner surfaces

316, 318 may generally correspond to any suitable distance. However, in several embodiments, the first gap 334 may generally be in a range of about 5 millimeters (mm) to about 50mm, such as about 10mm to about 40mm or about 10mm to about 30mm and any other subranges therebetween. Similarly, in several embodiments, the second gap 336 may generally be in the range of 0mm to about 30mm (such as 0mm to about 25mm or about 5mm to about 20mm and any other subranges therebetween).

It should also be appreciated that after the shear web inserts 183 are positioned between the first and

second shear webs

48, 146, the inserts 183 may be clamped or otherwise secured within the rotor blade assembly 100 to allow the bond paste 328 to cure.

The method 200 may further comprise coupling at least one first connection device 342 disposed on the second side 304 of the shear web insert 183 across a portion of the perimeter gap 331 defined between the first end 306 of the shear web insert 183 and the first shear web 48. A second connection device 344 is then coupled across a portion of the perimeter gap 331 defined between the first end 306 of the shear web insert 183 and the first shear web 48, the second connection device 344 being disposed on the opposite first side 302 of the shear web insert 183.

An additional step in the method 200 and shown in fig. 15 may include forming the angled perimeter interface 300 of the shear web insert 183 such that the perimeter gap 331 includes a first gap 334 defined between the perimeter of the first side 302 of the shear web insert 183 and the adjacent surface, and a second gap 336 is defined between the perimeter of the second side 304 of the shear web insert 183 and the adjacent surface.

As shown in fig. 16 and 17, perimeter gap 331 may be filled with bond paste 328 using an injection device 366. The injection device 366 may be any suitable structure that maintains contact with the perimeter gap 331 and allows for continuous flow of the bonding paste, such as a 'tip' or injection nozzle.

Further, as shown in fig. 18-20, each of the first and

second connection devices

342 and 344 may have a first clip 368 and a second clip 370, and further have a horizontal portion 372 and a vertical portion 374. The first clamp 368 horizontal portion 372 may be coupled to the inner surface 316 of the first side 317 of the rotor blade assembly and the second clamp 370 horizontal portion 372 may be coupled to the inner surface 318 of the opposite second side 319 of the rotor blade assembly. The vertical portions 374 of the first and

second clips

368, 370 may extend in opposite directions from the horizontal portion 372 a sufficient distance such that the vertical portions 374 of the first and second clips overlap. The coupling of the horizontal and

vertical portions

372, 374 of the first and

second clips

368, 370 may be accomplished using the bonding paste 328. Likewise, the first and

second clips

368, 370 may use a tapered ply 376. The first clamp 368 and the second clamp 370 may be configured to control bond thickness and may be installed during the same curing cycle as the blade insert 183.

Further, the

connection devices

342, 344 may be coupled to the

inner surfaces

316, 318 of the rotor blade assembly 100 such that the

connection devices

342, 344 are positioned adjacent to and/or otherwise engage the first side 302 and/or the first 304 of the shear web insert 183 at any shear web joint. The

connection devices

342, 344 may generally be configured to function as a means for retaining the shear web insert 183 within the rotor blade assembly 100. Additionally, the

connection devices

342, 344 may also be configured to function as a means for transferring loads between the shear web insert 183 and the

bodies

28, 114 of the rotor blade assembly 102 and/or blade insert 106.

It should be appreciated that the

connection devices

342, 344 may generally have any suitable configuration that allows

such devices

342, 344 to function as described herein. For example, the

connection devices

342, 344 may be configured similarly to the

positioning device segments

310, 312 described above, and thus may include a horizontal portion 346 configured to be coupled to the inner surfaces 316, 318 (e.g., using a suitable bonding paste or mechanical fasteners) and a vertical portion 348 extending substantially perpendicularly from the horizontal portion 346 so as to define a substantially "C" shaped structure when the vertical portions 374 of the first and

second clips

368, 370 overlap. However, in other embodiments, the

connection devices

342, 344 may have any other suitable configuration.

It should be appreciated by those of ordinary skill in the art that the particular views shown in the figures illustrate only one embodiment of the method 200 described herein. It should also be appreciated that although the shear web insert 183 is described as a single component, the insert 183 may be formed from a plurality of shear web segments coupled to one another within the rotor blade assembly 100. In particular, embodiments including a multi-piece shear web insert 183 may be advantageous when sufficient access to the interior of the rotor blade assembly 100 is not available via the

access windows

140, 141.

This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.

Claims

1. A method for connecting and repairing shear webs, the method comprising:

dry-fitting a shear web insert in a rotor blade assembly to establish a peripheral gap at an angled peripheral interface between the shear web insert and the rotor blade assembly, the angled peripheral interface being positioned between the shear web insert and at least one adjacent surface, the at least one adjacent surface including a first shear web, a second shear web, a first side of the rotor blade assembly and a second side of the rotor blade assembly, and

a bonding paste is injected into the peripheral gap.

2. The method of claim 1, further comprising:

coupling at least one first connection device across a portion of the peripheral gap, the at least one first connection device being disposed partially on a first side of at least one of the first and second shear webs; and

coupling at least one second connection device across a portion of the peripheral gap, the at least one second connection device being partially disposed on an opposing second side of at least one of the first and second shear webs.

3. The method of claim 1, further comprising:

coupling at least one first and second locator segment along an inner surface of at least one of the first or second sides of the rotor blade assembly for dry-fit positioning of the shear web insert, and

placing a plurality of spacers along at least one of a bottom surface, a first end, or a second end of the shear web insert, the plurality of spacers aligned in the peripheral gap along a first side of the shear web insert.

4. The method of claim 1, further comprising:

forming the angled peripheral interface such that a first gap is defined between a first side of the shear web insert and the at least one adjacent surface and a second gap is defined between a second side of the shear web insert and the at least one adjacent surface.

5. The method of claim 4, wherein the angled peripheral interface is configured such that the first gap is smaller than the second gap.

6. The method of claim 4, wherein the angle in the angled peripheral interface is in a range of about 0 degrees to about 50 degrees.

7. The method of claim 4, wherein the first gap is in a range of about 0 millimeters to about 30 millimeters and the second gap is in a range of about 5 millimeters to about 75 millimeters.

8. The method of claim 1, further comprising applying the bonding paste using at least one injection device comprising a cartridge and a nozzle.

9. The method of claim 1, further comprising spilling the bond paste from the peripheral gap such that it is extruded from the peripheral gap on both the first and second sides of the shear web insert.

10. The method of claim 2, wherein each of the at least one first and second connection devices comprises at least one prefabricated clamp, the at least one prefabricated clamp further comprising a horizontal portion and a vertical portion, the at least one prefabricated clamp horizontal portion coupled to at least one of an inner surface of a first side of the rotor blade assembly and an inner surface of an opposite second side of the rotor blade assembly.

11. The method of claim 10, wherein the vertical portions of at least two pre-clips extend from the respective horizontal portions in opposite directions a sufficient distance to couple with opposite vertical portions.

12. A rotor blade assembly for a wind turbine, the rotor blade assembly including a first side and a second side, wherein the first side of the rotor blade assembly corresponds to one of a pressure side or a suction side of the rotor blade assembly and the opposite second side of the rotor blade assembly corresponds to the other of the pressure side or the suction side of the rotor blade assembly, the rotor blade assembly comprising:

a first blade segment defining a joint end, the first blade segment including a first shear web with an angled interface at the joint end;

a second blade segment coupled to a joint end of the first blade segment, the second blade segment including a second shear web with an angled interface at the joint end;

at least one first connection device coupled across at least a portion of the joint end, the at least one first connection device coupled at least partially on a first side of at least one of the first and second shear webs;

at least one second connection device coupled across at least a portion of the joint end, the at least one second connection device at least partially coupled on an opposite second side of at least one of the first and second shear webs; and

a bonding paste infused into the angled interface.

13. The assembly of claim 12, further comprising:

a shear web insert positioned between the first shear web and the second shear web, the shear web insert defining a peripheral gap at an angled peripheral interface between the shear web insert and the rotor blade assembly, the angled peripheral interface being positioned between the shear web insert and at least one adjacent surface, the at least one adjacent surface including the first shear web, the second shear web, a first side of the rotor blade assembly, and a second side of the rotor blade assembly.

14. The assembly of claim 13, further comprising

At least one first and second positioning device segments coupled along an inner surface of at least one of the first or second sides of the rotor blade assembly; and

a plurality of spacers positioned along at least one of a bottom surface, a first end, or a second end of the shear web insert, the plurality of spacers aligned in the peripheral gap along a first side of the shear web insert.

15. The assembly of claim 14, wherein the angled peripheral interface comprises a first gap defined between a first side of the shear web insert and the at least one adjacent surface, and a second gap defined between a second side of the shear web insert and the at least one adjacent surface.

16. The assembly of claim 15, wherein the angled peripheral interface is configured such that the first gap is smaller than the second gap.

17. The assembly of claim 16, wherein the angle in the angled peripheral interface is in a range of about 0 degrees to about 50 degrees.

18. The assembly of claim 13, wherein the bond paste in the peripheral gap is configured to overflow the peripheral gap such that it is extruded from the peripheral gap on both the first and second sides of the shear web insert.

19. A connection device, the connection device comprising:

at least one precast clamp further comprising a horizontal portion and a vertical portion, the at least one precast clamp horizontal portion coupled to at least one of an inner surface of a first side of the rotor blade assembly and an inner surface of an opposing second side of the rotor blade assembly.

20. The connection device of claim 19, wherein the vertical portions of at least two pre-clips extend from the respective horizontal portions in opposite directions a sufficient distance to couple with opposite vertical portions.